BR112012008201A2 - aircraft engine assembly whose attachment beam comprises a structural wrapper forming an inner radial boundary of the secondary flow - Google Patents

aircraft engine assembly whose attachment beam comprises a structural wrapper forming an inner radial boundary of the secondary flow

Info

Publication number
BR112012008201A2
BR112012008201A2 BR112012008201A BR112012008201A BR112012008201A2 BR 112012008201 A2 BR112012008201 A2 BR 112012008201A2 BR 112012008201 A BR112012008201 A BR 112012008201A BR 112012008201 A BR112012008201 A BR 112012008201A BR 112012008201 A2 BR112012008201 A2 BR 112012008201A2
Authority
BR
Brazil
Prior art keywords
inner radial
secondary flow
structural
engine assembly
wrapper
Prior art date
Application number
BR112012008201A
Other languages
Portuguese (pt)
Inventor
Laurent Lafont
Original Assignee
Airbus Operations Sas
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations Sas filed Critical Airbus Operations Sas
Publication of BR112012008201A2 publication Critical patent/BR112012008201A2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
    • B64D27/40—
    • B64D27/404—
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]

Abstract

conjunto motor para aeronave, cuja longarina de afixação compreende um envoltório estrutural que forma delimitação radial interna do fluxo secundário. a presente invenção refere-se a um conjunto motor (1) para aeronave, compreendendo uma turbo-máquina com duplo fluxo (2) e uma longarina de afixaçaõ (4),a turbo-máquina compreendendo um envoltório estrutral (40) estendendo-se para baixo a prtir do cubo (20) de um cárter intermediária, esse envoltório (40) participando da delimitação radial interna de uma passagem (38) para um fluxo secundário (36) da turbo-máquina. além disso, a estrutura primária (46) compreende um envoltório estrutural (50), montado sobre o envoltório estrutural (40) e ajustada na continuidade abaixo desta, a fim de participar também na delimitação radial interna da passagem (38) para o fluxo secundário, a estrutura primária compreendendo , além disso, uma estrutura de desvio (52) disposta na passagem (38) e destinada a ligar o envoltório (50) a um elemento (6) da aeronave. também, o envoltório estrutural (50) integra um sistema de inversão de impulso (75).aircraft engine assembly, the attachment of which comprises a structural wrapper forming an inner radial boundary of the secondary flow. The present invention relates to an aircraft engine assembly (1) comprising a dual flow turbo engine (2) and a display stringer (4), the turbo engine comprising a structural wrapper (40) extending downwardly from the hub (20) of an intermediate crankcase, that casing (40) participates in the inner radial delimitation of a passageway (38) to a secondary flow (36) of the turbo machine. furthermore, the primary frame 46 comprises a structural wrapper 50 mounted on the structural wrapper 40 and adjusted in continuity below it to also participate in the inner radial delimitation of the passageway 38 for the secondary flow , the primary structure further comprising a bypass structure (52) disposed in the passageway (38) and intended to connect the wrapper (50) to an element (6) of the aircraft. Also, the structural wrapper (50) integrates an impulse inversion system (75).

BR112012008201A 2009-07-31 2010-07-29 aircraft engine assembly whose attachment beam comprises a structural wrapper forming an inner radial boundary of the secondary flow BR112012008201A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0955425A FR2948636B1 (en) 2009-07-31 2009-07-31 AIRCRAFT ENGINE ASSEMBLY INCLUDING A STRUCTURAL ENVELOPE FOR THE INTERNAL RADIAL DELIMITATION OF THE SECONDARY FLOW
PCT/FR2010/051617 WO2011012822A2 (en) 2009-07-31 2010-07-29 Engine assembly for an aircraft of which the attachment strut comprises a structural case forming an internal radial delimitation of the secondary flow

Publications (1)

Publication Number Publication Date
BR112012008201A2 true BR112012008201A2 (en) 2016-03-08

Family

ID=42046412

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012008201A BR112012008201A2 (en) 2009-07-31 2010-07-29 aircraft engine assembly whose attachment beam comprises a structural wrapper forming an inner radial boundary of the secondary flow

Country Status (6)

Country Link
US (1) US8646725B2 (en)
EP (1) EP2459445B1 (en)
CN (1) CN102481981B (en)
BR (1) BR112012008201A2 (en)
FR (1) FR2948636B1 (en)
WO (1) WO2011012822A2 (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2928180B1 (en) * 2008-02-28 2010-04-02 Airbus France AIRCRAFT ENGINE ASSEMBLY COMPRISING AN ANNULAR EFFORTS TRANSFER STRUCTURE SURROUNDING THE CENTRAL HOUSING OF A TURBOJET ENGINE.
FR2950322B1 (en) * 2009-09-22 2012-05-25 Airbus Operations Sas AIRCRAFT ENGINE FITTING ELEMENT, AIRCRAFT ASSEMBLY COMPRISING THE AIRCRAFT ELEMENT AND ASSOCIATED AIRCRAFT
FR2950323B1 (en) * 2009-09-22 2011-11-04 Airbus Operations Sas AIRCRAFT ENGINE HANDLING MACHINE, AN ASSEMBLY COMPRISING THIS MAT AND ASSOCIATED AIRCRAFT
FR2952922B1 (en) * 2009-11-20 2012-05-25 Snecma HANDLING ASSEMBLY FOR AN AIRCRAFT ENGINE MODULE
GB2492107B (en) * 2011-06-22 2013-09-04 Rolls Royce Plc Mounting assembly
FR2987347B1 (en) * 2012-02-28 2014-12-19 Snecma CUTTING PIECE FOR A REAR SUSPENSION OF A TURBOMOTEUR TO AN AIRCRAFT PYLON AND SUSPENSION COMPRISING SUCH AN ATTACHMENT PIECE.
FR2989952B1 (en) 2012-04-27 2014-04-18 Aircelle Sa TURBO BOREHOLE WITH DOWNSTREAM SECTION
FR2994942B1 (en) * 2012-09-06 2015-08-07 Airbus Operations Sas LATERAL PROPULSIVE ASSEMBLY FOR AIRCRAFT COMPRISING A SUPPORT ARM OF A TURBOMOTEUR.
FR3008136B1 (en) * 2013-07-04 2017-12-15 Snecma SUSPENSION OF A STRUCTURE IN A TURBOREACTOR BY A HYPERSTATIC MESH WITH PRE-TENSION BONDING ELEMENTS AND ASSOCIATED PRE-TENSIONING METHOD
FR3008070B1 (en) * 2013-07-08 2020-11-06 Astrium Sas REUSABLE LAUNCH VEHICLE THROTTLE BLOCK
GB201322048D0 (en) 2013-12-13 2014-01-29 Rolls Royce Deutschland A joint between components
FR3015569B1 (en) * 2013-12-19 2019-01-25 Safran Aircraft Engines CARTER FOR A PROPULSIVE ASSEMBLY
FR3048957B1 (en) 2016-03-15 2018-03-09 Airbus Operations AIRCRAFT ENGINE ASSEMBLY, COMPRISING SOFT DEVICES FOR TRANSMITTING EFFORTS AGENCIES BETWEEN THE THRUST INVERSION COVERS AND THE ENGINE
FR3065441B1 (en) * 2017-04-19 2019-07-05 Airbus Operations AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF A COUPLING MAT FIXED TO A SAILBOX USING A BOLT CONNECTION
FR3075174B1 (en) 2017-12-18 2020-12-11 Safran Aircraft Engines SUPPORTING STRUCTURE INTENDED FOR MOUNTING ON A GAS GENERATOR
FR3078109B1 (en) * 2018-02-16 2020-03-20 Safran Aircraft Engines FIRE RESISTANCE DEVICE FOR INTERPOSING BETWEEN AN UPSTREAM END OF AN AIRCRAFT TURBOMACHINE MOUNTING MAT, AND A TURBOMACHINE COVER DELIMITING AN INTER-VEIN COMPARTMENT
FR3078999A1 (en) * 2018-03-13 2019-09-20 Airbus Operations DOUBLE FLOW TURBOREACTOR COMPRISING A SERIES OF ROTATING BLADES TO SHUT THE VEIN FROM THE SECONDARY FLOW
FR3100529B1 (en) 2019-09-09 2021-08-27 Safran Aircraft Engines Together for an aircraft
US11518535B2 (en) * 2019-09-30 2022-12-06 Rohr, Inc. Nacelle cowl deflection limiter
CN111828196B (en) * 2020-07-04 2022-11-01 峰特(浙江)新材料有限公司 Aircraft engine exhaust nozzle
CN112572825B (en) * 2020-11-27 2022-12-13 北京星航机电装备有限公司 Aircraft tail cabin and assembly method thereof
CN112874793A (en) * 2021-04-02 2021-06-01 西安航空学院 Aeroengine connection structure and aeroengine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1249123A (en) * 1968-06-26 1971-10-06 Rolls Royce Ducted fan gas turbine engine
FR2478575A1 (en) * 1980-03-19 1981-09-25 Snecma DEVICE FOR PLACING A REACTOR IN AN AIRCRAFT CELL
FR2560854B1 (en) * 1984-03-07 1986-09-12 Snecma STRUCTURAL HOODS PARTICIPATING IN THE ASSEMBLY RIGIDITY OF A TURBO-JET
US4785625A (en) * 1987-04-03 1988-11-22 United Technologies Corporation Ducted fan gas turbine power plant mounting
US5226288A (en) * 1991-06-21 1993-07-13 Rohr, Inc. Torque link fan jet engine support for reducing engine bending
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
FR2759418B1 (en) * 1997-02-13 1999-03-19 Snecma PUSH INVERTER FOR VERY HIGH DILUTION TURBOSOFFICE
US5915651A (en) * 1997-07-10 1999-06-29 Mcdonnell Douglas Corporation Reverse thrust inlet vortex inhibitor
FR2866070B1 (en) * 2004-02-05 2008-12-05 Snecma Moteurs TURBOREACTOR WITH HIGH DILUTION RATE
FR2873986B1 (en) * 2004-08-04 2007-12-21 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY
FR2885877B1 (en) 2005-05-23 2008-12-12 Airbus France Sas AIRBORNE TURBOJET ENGINEERING MACHINE
FR2891250B1 (en) 2005-09-28 2007-10-26 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY COMPRISING AN ENGINE AND A HITCHING MACHINE OF SUCH AN ENGINE
FR2891254B1 (en) 2005-09-29 2007-10-26 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY
FR2903076B1 (en) * 2006-06-30 2009-05-29 Aircelle Sa STRUCTURING LUGGAGE

Also Published As

Publication number Publication date
CN102481981B (en) 2014-10-01
WO2011012822A3 (en) 2011-03-31
FR2948636A1 (en) 2011-02-04
EP2459445B1 (en) 2013-12-11
FR2948636B1 (en) 2012-01-13
EP2459445A2 (en) 2012-06-06
US20120111995A1 (en) 2012-05-10
WO2011012822A2 (en) 2011-02-03
US8646725B2 (en) 2014-02-11
CN102481981A (en) 2012-05-30

Similar Documents

Publication Publication Date Title
BR112012008201A2 (en) aircraft engine assembly whose attachment beam comprises a structural wrapper forming an inner radial boundary of the secondary flow
BR112014017200A2 (en) retaining geometry air filter element
BR112014017127A2 (en) air filter element with fixing geometry
ATE490917T1 (en) REAR LOWER AERODYNAMIC FAIRING FOR AN AIRCRAFT ENGINE MOUNTING DEVICE
BR112016007680A2 (en) satellite carrier and speed reducer with epicloid train
DE602007003981D1 (en) STRUCTURE GONDEL
BRPI0907478A2 (en) propulsion engine inlet flap for application to the air inlet of an aircraft propeller engine as well as propellant inlet and engine system inlet flap
BR112013016652A2 (en) nacelle for an aircraft dual flow turbojet engine
BRPI1010899A2 (en) SLIDING ELEMENT
BR112012011535A2 (en) mounting an agb into an intermediate housing for a turbojet fan enclosure
BR112015018986A2 (en) power generation system and method of operation of a power generation system
BRPI0903353A8 (en) EXHAUST GAS RETREATMENT DEVICE
IN2014DN07487A (en)
BR102012024670B8 (en) gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine
EP2537755A3 (en) Mounting assembly
BR112013008071B8 (en) FILTER DEVICE
BR112013021692A2 (en) turbine housing, including ring sector fastening means
BR112015011059A2 (en) installation of a fuel injection system with a fuel injection valve and a decoupling element
WO2013180960A3 (en) Exhaust-gas turbocharger
BR112015030086A2 (en) fuel supply system
WO2009024662A3 (en) Coupling system connecting an internal structure and an external structure of a jet engine nacelle
BR112014006236A2 (en) flap assembly of a turbo engine nacelle equipped with at least one electric defrost system and turbo engine nacelle
BR112018012139A2 (en) fuel cell system and control method for fuel cell system
BR112015011366A2 (en) method and device for acoustic detection of a malfunction of an engine equipped with active noise control
BR112014004578A2 (en) set formed by a turbomotor and its attachment system to an aircraft structure

Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 8A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2473 DE 29-05-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.